Numerical Investigation on Multiple Waves Propagation Mode of Rotating Detonation Waves

Abstract

A supersonic detonation compresses the premixed reactants using a leading shock to achieve spontaneous ignition and self-sustained propagation. In recent years, detonation-based combustion has received increased interest because the thermodynamic efficiency is higher than traditional deflagrationbased combustion system. One of the high speed propulsion concepts is based on rotating detonation wave (RDW), which derives to the Rotating Detonation Waves Engines (RDE). There have been significant progress of rotating detonation waves beginning with theoretical analyses, numerical simulations and experimental studies over the past few years. The detailed review of the physical flow process through the annular channel of RDEs have been studied here [1-4]. This work [5] reviewed the current status of experimental research of continuous detonation of fuel-air (C2H2-air, H2-air, and CO/H2-air) mixtures in annular combustors, which provide the effect of fuel-oxidizer compositions and combustor geometric parameters on the multi-waves and the total pressure of combustion products. However, the formation mechanism of multiple waves with different stagnation temperature and rotating detonation initiation pattern is still not clear. These characteristics are significant to understand the RDW dynamics and performance of the rotating detonation propulsion system. Motivated by these considerations, the two dimensional RDW flow structures are investigated via numerical simulations based on the reactive Euler equations. The focus of this study is the effect of inflow stagnation temperature, heat release rate and initiation on the wavelet pattern of RDW.